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<h1>DG-S Technical Specification</h1>
<h3>Primary Engine Subsystem</h3>

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<th rowspan=2>Thrust rating</th>
<th colspan=2 align=center>Flight model</th>
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<th align=center style="border-top: none; width: 10em">easy</th>
<th align=center style="border-top: none; width: 10em">complex</th>
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<td>Main thrust [kN]</td>
<td>2 x 180</td>
<td>2 x 150 (vacuum)<br>2 x 120 (1 bar)</td>
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<td>Retro thrust [kN]</td>
<td>2 x 34</td>
<td>2 x 34 (vacuum)<br>2 x 27.2 (1 bar)</td>
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<td>Hover thrust [kN]</td>
<td>3 x 83.3</td>
<td>3 x 66.7 (vacuum)<br>3 x 53.3 (1 bar)<sup>1</sup></td>
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<td>ISP [m/s]</td>
<td>4&middot;10<sup>4</sup></td>
<td>4&middot;10<sup>4</sup> (vacuum)<br>3.2&middot;10<sup>4</sup> (1 bar)</td>
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<sup>1</sup>) Requires total mass < 16300kg to allow vertical liftoff from Earth's surface.

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<th>Mass</th>
<th style="width: 10em">&nbsp;</th>
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<td>Empty mass [kg]</td>
<td>13.0&middot;10<sup>3</sup></td>
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<td>Main tank capacity [kg]</td>
<td>10.4&middot;10<sup>3</sup></td>
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<td>RCS tank capacity [kg]</td>
<td>600</td>
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<td>Scramjet fuel capacity [kg]</td>
<td>4.0&middot;10<sup>3</sup></td>
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<td>Max. takeoff mass [kg]</td>
<td>25.0&middot;10<sup>3</sup></td>
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<p>
<a href="DGscram.htm">Scramjet subsystem</a>
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